【摘要】：本文針對天基反航母武器的軌跡優(yōu)化及制導(dǎo)方法開展研究。以天基反航母武器到達(dá)航母初始位置上方設(shè)定位置的時間最短為性能指標(biāo),采用高斯偽譜法對天基反航母武器的再入飛行階段進(jìn)行軌跡優(yōu)化,這樣可以減少敵方的預(yù)警時間,實施快速突襲。考慮到再入飛行的中后段,特別是在對流層,天基反航母武器所經(jīng)歷的飛行環(huán)境變化大,氣動升力系數(shù)可能會出現(xiàn)不可忽視的攝動,導(dǎo)致飛行過程中出現(xiàn)較大的控制偏差。文中提出了一種考慮靈敏度的軌跡優(yōu)化算法,把終端狀態(tài)值對攝動系數(shù)的靈敏度加入到目標(biāo)函數(shù)中,并與時間最省指標(biāo)通過罰函數(shù)法結(jié)合到一起形成最終的優(yōu)化目標(biāo)。在對原來最優(yōu)性能指標(biāo)影響很小的情況下,可以有效減少因氣動升力系數(shù)的攝動而出現(xiàn)的落點偏差。這對進(jìn)入末端制導(dǎo)階段時導(dǎo)引頭迅速捕獲目標(biāo),確保精確擊中目標(biāo)具有重要意義。針對天基反航母武器的末端制導(dǎo)階段,推導(dǎo)出了天基反航母武器的制導(dǎo)指令信號。由設(shè)計出來的制導(dǎo)律,對天基反航母武器末端制導(dǎo)階段在MATLAB上進(jìn)行仿真,從仿真結(jié)果可以看出,由于天基反航母武器末端制導(dǎo)階段的初始飛行速度很高,一般是三倍以上音速,并且距離航空母艦并不十分遠(yuǎn),所以即使航空母艦以最高航速航行也難以躲避打擊,并且文中設(shè)計的末制導(dǎo)律涉及到的目標(biāo)信息容易在線測量,容易為制導(dǎo)計算機(jī)實現(xiàn)。
[Abstract]:In this paper, the trajectory optimization and guidance method of space-based anti-aircraft carrier weapon are studied. Taking the shortest time for space-based anti-aircraft carrier weapons to reach the set position above the initial position of the aircraft carrier, Gao Si pseudospectral method is used to optimize the trajectory of space-based anti-aircraft carrier weapons at the re-entry flight stage, so that the warning time of the enemy can be reduced. Carry out a quick raid. In view of the large changes in the flight environment experienced by space-based anti-aircraft carrier weapons especially in the troposphere the aerodynamic lift coefficient may appear unneglectable perturbation resulting in a large control deviation during flight. In this paper, a trajectory optimization algorithm considering sensitivity is proposed. The sensitivity of terminal state value to perturbation coefficient is added to the objective function, and the time saving index is combined with the penalty function method to form the final optimization target. Under the condition of little influence on the original optimal performance index, the fall point deviation caused by the perturbation of the aerodynamic lift coefficient can be effectively reduced. It is of great significance for the seeker to catch the target quickly and to make sure to hit the target accurately when it enters the terminal guidance stage. According to the terminal guidance stage of space-based anti-aircraft carrier weapon, the guidance command signal of space-based anti-aircraft carrier weapon is derived. Based on the designed guidance law, the terminal guidance phase of space-based anti-aircraft carrier weapons is simulated on MATLAB. From the simulation results, it can be seen that the initial flight speed of the terminal guidance phase of space-based anti-aircraft carrier weapons is very high, which is generally more than three times the speed of sound. And the distance from the aircraft carrier is not very far, so even if the aircraft carrier navigates at the highest speed, it is difficult to avoid the attack, and the target information involved in the terminal guidance law designed in this paper is easy to be measured online and easy to be realized by the guidance computer.
【學(xué)位授予單位】：南京航空航天大學(xué)
【學(xué)位級別】：碩士
【學(xué)位授予年份】：2016
【分類號】：V448.2

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本文編號：2266971